TCDS No.: EASA.IM.R.103
Model K-1200
Issue: 1
Date: 18 December 2014
TYPE CERTIFICATE
DATA SHEET
No. EASA.IM.R.103
for
Model K-1200
Type Certificate Holder
Kaman Aerospace Corporation
P.O. Box 2, Old Windsor Road
Bloomfield, Connecticut 06002
U.S.A.
For Model: Model K-1200 (K-MAX®)
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TCDS No.: EASA.IM.R. 103
Issue: 1
Model K-1200
Date: 18 December 2014
TABLE OF CONTENTS
SECTION 1: Model K-1200................................................................................................................................ 3
I. General ..................................................................................................................................................... 3
II. Certification Basis .................................................................................................................................... 3
III. Technical Characteristics and Operational Limitations ............................................................................ 4
IV. Operating and Service Instructions ......................................................................................................... 8
V. Notes ....................................................................................................................................................... 8
SECTION: ADMINISTRATIVE ............................................................................................................................ 11
I. Footnotes ............................................................................................................................................... 11
II. Acronyms and Abbreviations ................................................................................................................. 11
III. Type Certificate Holder Record ............................................................................................................. 12
IV. Change Record ..................................................................................................................................... 12
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TCDS No.: EASA.IM.R.103
Model K-1200
Issue: 1
Date: 18 December 2014
SECTION 1: Model K-1200
I. General
1.
Type/ Model/ Variant
1.1 Type
Model K-1200
1.2 Model
Model K-1200
1.3 Variant
---
2.
Airworthiness Category
Small Rotorcraft (Normal Category)
3.
Manufacturer
Kaman Aerospace Corporation
P.O. Box 2, Old Windsor Road
Bloomfield, Connecticut 06002
U.S.A.
4.
Type Certification Application Date
to FAA: 30 July 1990 (State of Design Authority)
to LBA: 6 May 1996
to ACG: 12 August 1999
5.
State of Design Authority
Federal Aviation Administration (FAA), USA
6.
Type Certificate Date
by FAA: 30 August 1994
by LBA: 15 November 1996
by ACG: 31 March 2000
7.
Type Certificate n°
by FAA: TR7BO
by LBA: 3069
by ACG: DF 010 – ACG
8.
Type Certificate Data Sheet n°
by FAA: TR7BO
by LBA: 3069
by ACG: DF 010 – ACG
9.
EASA Type Certification Date
28 September 2003,
in accordance with CR (EU) 748/2012, Article 3, 1.,
(a), 2nd bullet, 2nd indented bullet.
II. Certification Basis
1.
Reference Date for determining the
applicable requirements
2.
Airworthiness Requirements
30 July 1990
FAR Part 27 effective 1 February 1965 and amendments 27-1 through 27-28.
Maximum weight of 3 175 kg (7 000 lbs) without external load, approved 23 June 2005:
FAR Part 27, effective 1 February 1965 and Amdts. 27-1 through 27-37, except FAR 27.561(c),
27.865(b)(3)(ii) and 27.1365(c).
Compliance with instrument flight rules (IFR) operational requirements of Appendix B to
FAR 27.
Personnel carrying device system (PCDS):
applicable portions of FAR 27.865, Amdt. 27-36 for human external cargo (HEC).
3.
Special Conditions
none
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TCDS No.: EASA.IM.R.103
Model K-1200
Issue: 1
Date: 18 December 2014
4.
Exemptions
Grant of Exemption from FAR 27.1(a), Exemption
n° 6433 (Regulatory Docket n° 009SW), dated
25 April 1996 (maximum weight 2 948 kg (6 500 lbs)
5.
(Reserved) Deviations
none
6.
Equivalent Safety Findings
FAR 29.173(b)
7.
Requirements elected to comply
Compliance with the falling and blowing snow
requirement of FAR 27.1093(b)(1)(ii) has been
established
8.
Environmental Protection Requirements Emissions:
ICAO, Annex 16, Volume II, Amdt. 3, Part II for the
prevention of intentional fuel venting.
Noise:
ICAO Annex 16, Volume I, Amdt. 4.
Neither Chapter 8 nor 11 are applicable because this
helicopter is specifically designed and used for
agricultural, fire-fighting or external load-carrying
purposes. Therefore, there are no noise certification
levels for this product and there is no need to issue
a TCDSN.
III. Technical Characteristics and Operational Limitations
1.
Type Design Definition
K-1200 Engineering Description
2.
Description
Single gas turbine engine; two 2-bladed main rotors
based on the “Kaman Intermeshing System”, driven
by twin shafts of a single transmission; empennage
without tail rotor; fuselage of metal-composite
structure with tricycle-type landing gear.
3.
Equipment
The basic required equipment, as prescribed in the
applicable airworthiness regulations (see
Certification Basis), must be installed in the
helicopter for certification.
In addition, the following approved RFM is required:
Kaman K-1200 Helicopter Rotorcraft Flight Manual
(see Section IV number 1).
Furthermore the national regulations have to be
taken into account and built in before registration.
Additionally all equipment is certified when:
- it is mentioned in an FAA-approved Rotorcraft
Flight Manual Supplement to the under section IV
mentioned Rotorcraft Flight Manual, and,
- the certification basis is met, and,
- it is FAA-approved before, or EASA-approved, after
1 December 2006.
See also the K-1200 Master Minimum Equipment
List (MMEL) which is FAA-approved before
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Model K-1200
Issue: 1
Date: 18 December 2014
1 December 2006.
4.
5.
Dimensions
4.1 Fuselage
Length:
12.70 m
Width LDG gear: 3.80 m
Height:
4.01 m
4.2 Main Rotor
Diameter:
4.3 Tail Rotor
none
14.07 m
Engine
5.1 Model
Honeywell (Textron Lycoming)
1 x T5317A-1
5.2 Type Certificate
FAA TC/TCDS n°: E17EA
LBA TC/TCDS n°: 7027
EASA TC/TCDS n°: n/a
5.3 Limitations
5.3.1 Installed Engine Limits
Engine torque
pressure [hPa (psi)]
Gas generator
speed limits*
Exhaust Gas
Temperature (T9)
TKOF
(5 min)
4 482 (65)
26 400
(105.0%)
648°C
Max
Continuous
4 206 (61)
25 400
(101.0%)
626°C
* 25 150 rpm = 100%
5.3.2 Transmission Torque Limits
(Torque Pressure)
6.
No external load
[hPa (psi)]
With external load
[hPa (psi)]
TKOF
2 758 (40)
3 999 (58)
for 0 – 25 KIAS
3 103 (45)
for >25 KIAS
Max
Continuous
2 758 (40)
3 103 (45)
for 0 – 80 KIAS
Fluids (Fuel/ Oil/ Additives)
6.1 Fuel
Grades JP-4, JP-5 and JP-8.
Jet A, Jet A-1 and Jet B.
See Note 1 and Note 2.
6.2 Oil
Engine:
Type MIL-L-7808 or MIL-L-23699 (see Note 3)
Transmission: Dexron II or Dexron III
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Model K-1200
Issue: 1
6.3 Additives
7.
Date: 18 December 2014
See Note 2
Fluid capacities
7.1 Fuel
Fuel tank capacity: 865 litres (228.5 US gal)
Usable fuel:
830 litres (219.5 US gal)
at 4 111 mm (161.83 in) after datum (see Note 4).
8.
7.2 Oil
Engine:
12.1 litres (3.21 US gal)
Transmission: 12.1 litres (3.21 US gal)
7.3 Coolant System Capacity
n/a
Air Speeds Limits
8.1 Air Speed Limits
VNE PWR ON:
no external load:
100 KIAS, sea level to 5 000 ft (1 524 m) DA1;
90 KIAS, sea level to 8 000 ft (2 438 m) DA²,
(IFR, see Note 5)
with external load:
80 KIAS, sea level to 5 000 ft (1 524 m) DA1
70 KIAS, sea level to 5 000 ft (1 524 m) DA1
(with HEC, see Note 6)
VNE PWR OFF: 80 KIAS, sea level to 5 000 ft (1 524 m) DA1
1,
Footnote ²: see ‘SECTION: ADMINISTRATIVE’
9.
8.2 Ground Speed Limits
Maximum with nose wheel:
locked
25 kts
unlocked 10 kts
Rotor Speed Limits
Power on:
Maximum 105% Nr
(273 rpm)
100% Nr
(260 rpm)
for ground extended operations
Minimum 100% Nr
(260 rpm)
for MTOW ≤ 3 175 kg (7 000 lbs)
104% Nr
(270 rpm)
for MTOW > 3 175 kg (7 000 lbs)
104% Nr
(270 rpm)
for MTOW > 3 175 kg (7 000 lbs)
above 10 000 ft (3 048 m) DA
Power off:
Maximum 100% Nr
Minimum
75% Nr
(260 rpm)
(195 rpm)
10.1 Altitude
15 000 ft
12 000 ft
VFR day and night
IFR
10.2 Temperature
-32°C (-25.6°F) to +48.9°C (120°F)
10. Maximum Operating Altitude and
Temperature
11. Operating Limitations
(4 572 m)
(3 658 m)
- VFR day and night,
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Model K-1200
Issue: 1
Date: 18 December 2014
- IFR, national operating rules have to be followed,
- HEC (see Note 6),
- Flights under icing conditions are prohibited,
- Acrobatic manoeuvres are prohibited.
12. Maximum Weight
No external load:
3 175 kg (7 000 lbs), see Note 7, 8 and 12.
With external load:
5 443 kg (12 000 lbs)
13. Centre of Gravity Range
C.G. behind STA 0
[mm (in)]
Gross Weight
[kg (lbs)]
4 242 (167.0)
2 268 - 5 443
(5 000 - 12 000)
4 305 (169.5)
5 443 (12 000)
4 343 (171.0)
3 175 (7 000)
4 369 (172.0)
2 722 - 2 268
(6000 - 5000)
Lateral C.G. limits
[mm (in)]
± 32 (1.25)
Straight-line variation between points.
14. Datum
The datum line (STA 0) is located at 159 mm (6.265 in)
forward of nose.
15. Levelling Means
No levelling plate.
Level at cockpit door sill per instructions in Section
08-00-00 of Kaman Model K-1200 K-MAX Maintenance
and Servicing Instructions, Manual KMM.
16. Minimum Flight Crew
1 pilot, at 2 743 mm (108.0 in) behind datum
17. Maximum Passenger Seating
Capacity
n/a, (single seater)
18. Passenger Emergency Exit
None, (single seater)
19. Maximum Baggage/ Cargo Loads
Baggage compartment:
226 kg (500 lbs)
Cargo floor loading:
488 kg/m² (100 lbs/ft²)
20. Rotor Blade Control Movement
For rigging information, refer to Section 67-00-00 of
Kaman Model K-1200 K-MAX Maintenance and Servicing
Instructions, Manual KMM.
21. Auxiliary Power Unit (APU)
n/a
22. Life-limited Parts
Refer to Chapter 04 “Airworthiness Limitations” of Kaman
Model K-1200 K-MAX Maintenance and Servicing
Instructions, Manual KMM.
23. Wheels and Tyres
3-wheel tricycle landing gear (1 nose, 2 main)
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Model K-1200
Issue: 1
Date: 18 December 2014
IV. Operating and Service Instructions
1.
Flight Manual
Kaman K-1200 Helicopter Rotorcraft Flight Manual, FAAapproved 30 August 1994, or subsequent approved³
revisions.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
2.
Maintenance Manual
Kaman Model K-1200 K-MAX Maintenance and Servicing
Instructions, Manual KMM.
3.
Structural Repair Manual
None
4.
Weight and Balance Manual
Section 07 of Kaman K-1200 Helicopter Rotorcraft Flight
Manual, FAA-approved 30 August 1994, or subsequent
approved³ revisions.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
5.
Illustrated Parts Catalogue
Kaman Model K-1200 K-MAX Parts Catalogue
6.
Service Letters and Service
Bulletins
As published by K-1200 K-Max Publication List
7.
Required Equipment
Section 07 of Kaman K-1200 Helicopter Rotorcraft Flight Manual lists removable items. All
other equipment required. FAA-approved 30 August 1994 or subsequent approved³ revisions.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
8.
Wiring Diagram Manual
K-MAX Wiring Diagram Manual, Rev. 1,
dated 1 December 2011.
V. Notes
1.
See Section 10 of the approved³ Rotorcraft Flight Manual for the complete listing of approved
Jet A, Jet A-1, Jet B, MIL-T-5624 and all equivalent fuels. Equivalent fuel:
- MIL-T-83133, Grade JP-8, may also be used.
- Use of kerosene fuels (JP-4 or JP-5) should be avoided when starting at ambient
temperatures below -12°C (10°F).
- Commercial fuels made to conform to ASTM Specification D 1655 do not contain anti-icing
additives unless specified by bulk purchaser. Care must be taken with these fuels with
respect to water contamination and flight conditions.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
2.
Anti-icing, anti-corrosion and biocidal additives specified in Section 10 of the approved³
Rotorcraft Flight Manual may be used singly or in any combination. The specified additives
should not be added to fuel MIL-T-5624, Grades JP-4 and JP-5, or to fuel MIL-T-83133, Grade
JP-8, since they are already present in these fuels.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
3.
Approved engine oil brands are listed in Section 10 of the approved³ Rotorcraft Flight Manual.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
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V. Notes (contd.)
4.
Current weight-and-balance report, including list of equipment included in certificated empty
weight, and loading instructions, when necessary, must be provided for each type helicopter
at the time of original certification.
See approved³ Rotorcraft Flight Manual loading section for fuel weight and moment-arm
variations with fuel type and fuel quantity.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
5.
Operation under the instrument flight rules (IFR) of Appendix B of FAR 27 approved 14 May
1999. See approved³ Rotorcraft Flight Manual for limitations, operational requirements,
required equipment, and weight-and-balance considerations.
6.
A personnel carrying device system (PCDS) for carrying human external cargo (HEC) was
approved 13 February 1998. The PCDS is limited to carriage of personnel that is a flight
crewmember or a flight crewmember trainee or that performs an essential function in
connection with the external-load operation or that is necessary to accomplish the work
activity directly associated with that operation. See approved³ Rotorcraft Flight Manual for
limitations, operational requirement, a weight-and-balance considerations.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
7.
The helicopter is certificated for special operations of (approved 9 June 1995):
- Agriculture as defined in the following paragraph:
Agricultural aircraft operation means the operation of an aircraft for the purpose of (1)
dispensing any economic poison, (2) dispensing any other substance intended for plant
nourishment, soil treatment, propagation of plant life, or pest control, or (3) engaging in
dispensing activities directly affecting agriculture, horticulture, or forest preservation, but
not including the dispensing of live insects.
- Dispensing of fire fighting materials; and
- Carrying external loads as defined in the national applicable rules.
The special purpose operations may be conducted at maximum weights above 2 722 kg
(6 000 lbs) up to and including 2 948 kg (6 500 lbs).
8.
Grant of Exemption n° 6433, dated 25 April 1996, allows increase in maximum gross weight
from 2 722 kg (6 000 lbs) to 2 948 kg (6 500 lbs) while maintaining the original rotorcraft
certification. The exemption is subject to the following conditions and limitations:
- The design of the helicopter cannot be changed to add passengers as part of the gross
weight increase.
- Prior to exercising the privileges of the exemptions, each K-1200 helicopter (for which
exemption is sought) and all modifications made to it, must meet the requirements
established in the current certification basis, at the increased gross weight. This includes any
special requirements for certification: i.e. equivalent levels of safety and special conditions
that may have been issued to complete certification.
- All operations above 2 722 kg (6 000 lbs) must be limited to agricultural operations as
defined in Note 7; dispensing firefighting materials; or carrying external loads as defined in
national applicable rules; unless a noise test is conducted prior to increasing the gross weight
above 2 722 kg (6 000 lbs).
9.
The conduction of the engine air for the cab heating has to be modified according to Kaman
K-1200 K-MAX Service Bulletin No. 044.
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Model K-1200
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Date: 18 December 2014
V. Notes (contd.)
10. All placards required in the approved³ Rotorcraft Flight Manual must be installed in the
appropriate locations. The following placard must be displayed in front of and clear view of
the pilot:
“THIS AIRCRAFT MUST BE OPERATED IN COMPLIANCE WITH THE OPERATING LIMITATIONS
SPECIFIED IN THE APPROVED³ FLIGHT MANUAL.”
11. Information essential to the proper maintenance of the helicopter is contained in the Kaman
Model K-1200 K-MAX Maintenance and Servicing Instructions, Manual KMM, provided with
each helicopter. The values of retirement (service) life contained in Chapter 04 or inspection
intervals cannot be increased without official approval³.
Footnote³: see ‘SECTION: ADMINISTRATIVE’
12. Original certification basis limited maximum weight to 2 722 kg (6 000 lbs) or less.
Special purpose operation (see Note 7) permitted operation to 2 945 kg (6 500 lbs) pending
Grant of Exemption n° 6433 (see Note 8).
FAR, Part 27, Amdt. 37, changed the maximum weight to 3 171 kg (7 000 lbs) or less.
Maximum weight of 3 171 kg (7 000 lbs) without external load approved 23 June 2005 by FAA.
13. Designation:
Kaman K-MAX® is used as marketing designation for Kaman K-1200 helicopters.
14. Manufacturer's serial numbers:
A94-0002, A94-0004 and up are eligible.
***
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Model K-1200
Issue: 1
Date: 18 December 2014
SECTION: ADMINISTRATIVE
I. Footnotes
* Primary Certification Authority certification application date for grandfathered products.
1
Decrease 3 kts (5.6 km/h) per 1 000 ft (305 m) above 5 000 ft (1 524 m) DA.
² Decrease 3 kts (5.6 km/h) per 1 000 ft (305 m) above 8 000 ft (2 438 m) DA.
³ Approving Authority for the Rotorcraft Flight Manual, Rotorcraft Flight Manual Supplements and
Chapter 04 “Airworthiness Limitations” of the Maintenance Manual is:
- before 28 September 2003, the FAA,
- from 28 September 2003 to 1 December 2006, the FAA and the EASA, and;
- after 1 December 2006 the EASA.
The competent authorities of the EU Member States (e.g. LBA, ACG) are also approving Authority
for these documents before 28 September 2003.
II. Acronyms and Abbreviations
ACG
AMDT.
ASTM
C.G.
CR
DA
DP
EASA
EU
FAA
HEC
IFR
IPC
KIAS
LBA
LDG
MAX
MCP
MM
MMEL
PWR
RFM
S/N
SEC
STA
TCDS
TCDSN
TKOF
VFR
VNE
Austro Control, AU
Amendment
American Society for Testing and Materials
Centre of Gravity
(European) Commission Regulation
Density Altitude
Datum Point
European Aviation Safety Agency
European Union
Federal Aviation Administration
Human External Cargo
Instrument Flight Rules
Illustrated Parts Catalogue
Knots Indicated Air Speed
Luftfahrt-Bundesamt, DE
Landing
Maximum
Maximum Continuous Power
Maintenance Manual
Master Minimum Equipment List
Power
Rotorcraft Flight Manual
Serial Number
Seconds
Station
Type Certificate Data Sheet
Type Certificate Data Sheet Noise
Take-Off
Visual Flight Rules
Never Exceed Speed
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Model K-1200
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Date: 18 December 2014
III. Type Certificate Holder Record
Type Certificate Holder
Period
Kaman Aerospace Corporation
P.O. Box 2
Bloomfield, Connecticut 06002
U.S.A.
Since
30 August 1994
IV. Change Record
Issue
Date
Changes
TC issue
Issue 1
18 Dec 2014
Transfer of grandfathered FAA TCDS TR7BO into
EASA format
Initial EASA Issue
18 Dec 2014
- End of File -
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